Controlling apparatus for aircraft



Jan. 1, 1935. w. MOLLER CONTROLLING APPARATUS FOR AIRCRAFT :5 Sheet s-Sheet 1 Filed Aug. 4, 1934 Inventor.-

L AI/////// A '3 Sheets-Sheet 2 w. M0LLE| CONTROLLING APPARATUS FOR AIRCRAFT Filed Aug. 4. 1934 Jan. 1, 1935.

lnvenfor:

Jan. 1, 1935. w. MOLLER 1,986,761

CONTROLLING APPARATUS F01 AIRCRAFT Filed Aug. 4, 1934 3 Sheets-Sheet 3 triwgmm W Patented'Jan. 1, 1935 UNITED STATES, PATENT OFFICE oonrnonrmc APPARATUS FOR Amcmr'r Waldemar -Miiller, Klein-Machnow, near, Berlin, Germany, asslgnor to Askania-Werke A. G. yormals Central Werkstatt Dessau und Carl Bamberg-Friedenau, a German company Application August 4,1934, Serial No. 738,519 In Germany August 2, 1933 .12 Claims. (CL 244-29) This invention relates to. automatic controlling required for operation of said controlling means apparatus,,more particularly automatic steering than can be delivered by said resilient connection apparatus for aircraft. of said two levers, said levers will separate scis- In the case of heavy aircraft, automatic consorlike. As the aircraft starts to come back upon trolling apparatus heretofore used have not alits course under the action of its steering means 5 ways proven adequate to keep the aircraft on its or rudder, said measuring or controlling means true course where pendulating occurs, particualso goes back' and thus influences said power larlyin squally weather. This is due to the fact controlling means to move the rudder to steer the that in the case of heavy aircraft the latter in reaircraft in the opposite direction a considerable l0 turning to thepcorr ect course under the corrective time before the aircraft itself has returned to the influence 'of the automatic controlling apparatus, correct course. acquiresa considerable angular velocity in its The invention and its aims and objects will be 'retum movement. In turning about its upright readily understood from the following descripaxis for example, the aircraft, even when auto tion taken in connection with the accompanying l5 matic restoring apparatus is used, reaches the drawings of one embodiment of the invention correct course with a not incori'siderable angular herein given for illustrative purposes, the true velocity, owing to the relatively slight resistance scope of the invention being more particularly offered to the turning movement by the air. This pointed out in the appended claims.

causes the aircraft to swing beyond the true Inthe illustrativeembodiment of the invention course, resulting in a pendulating movement, so the controlling means for controlling the power 20 that as stated the aircraft cannot steer a true serving to drive the steering mechanism 0on course, particularlyin squally weather. veniently comprises a pressure fluid jet nozzle The present invention aims "to correct these which may be similar to that shown in German defects and in the illustrative embodiment of the Patent No. 574,705. Referring to said patent,

invention herein described and illustrated,-thisis said'jet nozzle'is -rotatable about a vertical axis 25 conveniently accomplished by an arrangement and its discharge opening can play before two whereby one or more of the controlling or measintake ports which communicate respectively with uring devices which act upon the controlling the opposite; ends of a cylinder containing a means for the power that drives the steering piston suitably connected to the rudder or other mechanism are interconnected with said power flight controlling means of the aircraft. The 30 controlling means by a resilient or yieldingconjet nozzle delivers a continuous jet of pressure nection, whereby said controlling or measuring fluid, preferably compressed air which may he means will influence said power controlling supplied thereto by a compressor driven by the means to turn the rudder in the opposite direcaircraft motor, or from any other suitable source.

tion even before the aircraft has been returned to When the opening of the jet nozzle is directly 35 the true course under the influence of the correcin front of said two intake ports, so that each of tive action referred to. The yielding connection said ports receives the same amount of pressure may, for example, be inserted in the lever or link fluid, the piston in said cylinder will remain system which transmits the action of the measurstationary. 0n the other hand, said piston, and

ing or controlling means to said power controlling consequently the rudder will be moved in the 40 means, whereby the action of said measuring or one or the other direction according as the one controlling means upon said power controlling or the other of said intake ports receives more means effects a shortening or lengthening of said fluid pressure, consequent upon deviation of said lever or link system. If, for example, said measjet nozzle in the one or the other direction from uring or controlling means acts upon said power its median position. The position of said jet 45 controlling means by the rotation of a lever, two nozzle is controlled by co trolling or measuring levers may, in accordance with the present inmeans which are rendered operative responsive vention. be Substituted r said single lever, said to deviation of the aircraft from the correct two levers beingslidable relatively to each other course and/or to speed of turning movement of and connected together by a resilient connection the aircraft and/or acceleration of such turning 5 and provided also with damping means. When movement, in case of course steering for examthe measuring or controlling means acts, said ple, by a compass, that is to say by the differenpower controlling means will be actuated by said tial pressure diaphragm of a pneumatic comresilient connection, When said controlling pass, and preferably also by a direction indim a s r a e s e d position o mor p wer is cater. Restoring means is also preferably pro- .5

said part 8 and into said vided conveniently comprising a spring for example which is tensioned by the lateral movements of the lateral rudder in such manner that forces of determined strengths, respectively, delivered by corresponding variations or movements of said diaphragm and/or of said direction indicator, are required in order to restore said jet nozzle to its median position between said two intake ports.

Referring to the drawings:

' Figs.'1 and 2 show a side and end view, respectively, of the jet nozzle and its mounting;

Figs. 3, 4 and 5 show the mode and manner of connecting said jet nozzle with the controlling or measuring means, the compass diaphragm;

Figs. 6 to 8 illustrate details.

Referring to Figs. 1 and 2, the power controlling means, more specifically the jet nozzle 1, is connected to a hollow shaft 2 having its lower end mounted for rotary movement in a suitable ball bearing in a bottom plate 3. The upper end of said shaft 2 is also mounted in ball bearings provided in the upper wall of 2. preferably hollow square rod 4. The lower wall of said rod 4 is provided with a suitable packing through which said shaft 2 extends. Adjacent its upper end and within said hollow rod 4, said shaft 2 is provided with lateral ports 5-5 for compressed air. Compressed air may be supplied to the interior of said rod 4 from any suitable source of supply (not shown) through a pipe fitting 6, conveniently mounted for rotation about the closed end 6a of said rod 4 and communicating with the interior of the latter through ports 7a provided in the wall of said rod. A bracket consisting of two parts 7 and 8 suitably recessed to receive the squared portion of said rod 2, is clamped to said rod by screws 9 screwed through part 7. The free end of the part 7 of said bracket is recessed or bifurcated to receive one end of a lever 10 pivoted upon a stud or pin 11 extending through said part 7 (Figs. 3 and 4).

Means are provided to adjust said jet nozzle in its zero position relatively to the controlling or measuring means, herein the diaphragm chamber of the compass. Said means herein comprises a yoke 12 rigidlysecured to said bracket 7 and having set screws 13 mounted in its two flanges and adapted .to engage said lever 10 upon opposite sides. Lock nuts 14 may be provided better to preserve the-adjustment 'of said set screws. Said lever 10 may thus be adjusted in any desired angular position relatively to said jet nozzle.

The diaphragm chamber-15 controlled by the pneumatic compass is contained in an airtight fixed casing 16, one of the compressed air supply passages (not shown), controlled by said compass, opening into said chamber 16 and, the other, into said diaphragm chamber 15. Movements in the diaphragm of said diaphragm chamber serve to rotate a shaft 19 through lever system 17, 18 connecting said diaphragm to said shaft. Said shaft 19 is provided with a portion 19a which is rectangular in cross section and carries a lever 20. To a lateral wall 21 of the apparatus there is suitably secured a bracket 22 having projecting arms 21a, 22a and 23a in which are suitably journaled two aligned shafts 23 and 24. Levers 25 and 26 are rigidly secured at one end to said shafts 23 and 24 respectively. One of said levers, the upper one 25 for example, is connected by a link 27 to lever 10 and consesee Fig. 6, are mounted said spindle, see Fig. 4. The

quently to said jet pipe, while the other lever, lever 26 for example, is connected by a link 28 to lever 20 and consequently to the diaphragm of said diaphragm chamber. Said two levers 25 and 26 would preferably be of trapezoid shape in cross section, their wider surfaces facing each other as shown in Fig. 6; Two arms 31 and 32, for rotary movement upon spindles 35 and 36 suitably mounted in a connecting piece 34. Said arms 31, 32 are drawn toward each other by a spring 33 adjustably connected thereto at its two ends in holes 60, 61, and at their free ends said arms are provided with rollers 37, 38, respectively, which engage levers 25 and 26 at opposite sides and tend to maintain said levers in superposed position. Said connecting piece 34 is rotatable about a vertical shaft 40 mounted in a carriage 41 which is adapted to slide lengthwise of two rods 43, 44 secured to and projecting from said wall 21. Movement or adjustment of said carriage 41 lengthwise of said rods 43, 44 may be effected by suitable means, said means herein conveniently comprising a screw threaded spindle 45, see Fig. 4, which is journaled at its opposite portions 44a, 44b of the frame, its screw threaded portion engaging a screw threaded opening in said carriage 41, see Fig. 6. The free end of said spindle 45 may be provided with a squared head 45:: to facilitate rotation of by a suitable key (not shown). Yielding locking means will be provided, yieldingly to hold said spindle in adjusted position, said locking means herein conveniently comprising a spring pressed pawl 47 engaging a pinion 46 upon one end of levers 31 and 32 may thus be moved or adjusted longitudinally of said levers 25 and 26.

In accordance with the invention, damping means will preferably be provided connecting said lever 10, which is connected to said jet nozzle 1 and said lever 18 which is connected to said diaphragm chamber diaphragm. Any suitable damping means may be provided without departing from the scope of the invention. In the illustrative embodiment of the invention shown, said damping means conveniently comprises a damp-.

ing cylinder 53 carried by a bracket 54 screwed to standards 51, 52 carried by lever 10. A piston 55 working in said cylinder 53 has its rod 56 diaphragm of the chamber 15 and, through the squared portion of the shaft 19, will rotate the lever 20. The levers 31 and 32, held together by the spring 33, will turn the lever 26 and consequently the lever 10 and the spray nozzle 1. As soon as said nozzle reaches the end of its stroke which is determined by a stop, said levers 25 and 26 separate scissorlike, said lever 25 remaining stationary while saidlever 26, in response to the further movement of said diaphragm will continue to be moved in the one or the other direction. The damping system 55 will also be moved slowly relatively to the damping cylinder in correspondence to the damping adjustment. If now the pneumatic compass goes back said diaphragm immediately begins to carry back said jet nozzle, for the reason that said damping cylinder at first operates as a rigid connection. The rudder will therefore be moved to a reverse steering position. even before the aircraft has rethose of levers 31 and 7 tion or other injurious action whatsoever,

power operation of said mechanism;

means in a direction turned to the zero position. Said rudder willbe held in such reverse steering position until said damping cylinder yields gradually. By suitable adjustment of the damping and of the spring action the degree and length of said reverse steering action can be suitably determined and regulated. Adjustment of the actionpf the spring 33 can be effected by providing a plurality of securing points, such as holes 60, 61 in the levers 31, 32. A fine adjustment is obtained by the adjustability of the carriage 41 by means of the screw spindle 45. varying, lengthwise of the levers 25 and 26, the point at which the rollers 3'7 and 38 engage said levers, said point of engagement being thus adjusted nearer to or further away from the fulcrums of said levers. In order that such operation may be effected, free from any binding acthe fulcrum of the connecting member 31 as well as 32 are carried by the carriage 41. Means are also provided for the preliminary adjustment of the tension of spring 33. In the embodiment of the invention'herein described for illustrative purposes, this may be provided for by tapering saidlevers 25 and 26 in the direction of their fulcra as, in most cases such preliminary increase or decrease in the tension of said spring will have to be effected simultaneously with the shortening or lengthening of the effective length of said levers 25, 26.

It is to be understood that the present invention may be embodied in other specific forms without departing. from the spirit or essential attributes of said invention, and I therefore desire that the present embodiment be considered in all respects as illustrative and not restrictive. reference being had to rather than to the foregoing description to indi' cate the scope of the invention.

the appended claims I claim:

1. Automatic controlling apparatus, more par-J ticularly for aircraft, comprising, in combination, flight controlling means; power operated operating mechanism therefor; means to control the automatic means to act upon said power operation controlling means to move said flight controlling to return the aircraft to its course upon its deviation therefrom; andmeans, including a resilient *connection and damping means between'said automatic means and said power operation c ntrolling means, whereby said flight controlling means will be moved in the oppositedirection before the aircraft has returned to its course.

, Automatic controlling apparatus, more particularly for aircraft, comprising, in combination, flight controlling means; power operated operating mechanisnftherefor; measuring means to exert an automatic controlling action upon said power operation controlling means; and means including a resilient connection and damping means between said measuring means and said power operation controlling means.

3. Automatic controlling apparatus, more particularly for aircraft, comprising, in combination, flight controlling means; power operated operating mechanism therefor; measuring means to exert an automatic controlling action upon said power operation controlling means; means including a resilient connection and damping means between said measuring means andsaid power operation controlling means;

and means preliminarily to adjust said measuring means.

Such adjustment results in 4. Automatic controlling apparatus, more particularly for aircraft comprising, in combination, flight ing mechanism therefor; measuring means to exert an automatic controlling action upon saidpower operation controlling means; and intermediate connections between said measuring means and said power operation controlling means, including two levers relatively rotatable about a common fulcrum and connected by a controlling means; power operated operatresilient connection and an intermediate damping means.

5. Automatic controlling apparatus, more particularly for aircraft, comprising in combination, flight controlling means; power operated operating mechanism therefor; measuring means to exert an automatic controlling action upon said power operation controlling means; and operative connections between said measuring means and said power operation controlling eans including two levers relatively rotatable about a common fulcrum; a connecting member; two arms pivoted at one end to said connecting member and adapted withtheir other ends to engage said two levers and maintain themin alignment; and a spring connecting said two arms.

6. Automatic controlling apparatus, more par-,

ticularly for aircraft, comprising in combination, flight controlling means; power operated operating mechanism therefor; measuring means to exert anautomatic power operation controlling means;" operative connections between said measuring means and said power operation controlling means including two levers relatively rotatable about a common fulcrum: a rotatable connecting member; two arms pivoted at one end'to said connecting memher and adapted to engage said two levers and maintain them in alignment; and means to adjust the points of engagement of said arms with said levers longitudinally of the latter.

'7. Automatic controlling apparatus, more particularly for aircraft, comprisingin' combination, flight controllingmeans; power operated operating mechanism therefor; measuring means to exert an automatic controlling action upon said power operation controlling means; operative connections between said measuring means and said power operation controlling means comprising two levers relatively rotatable about a common fulcrum; means to engage said two levers and maintain them in alignment; and means yieldingly to maintain said last named means in engagement with said'two levers.

8. Automatic controlling apparatus, more particularly for. aircraft, comprising in combination, flight controlling means; power operated operating mechanism therefor; measuring means to exert an automatic controlling action upon said power operation controlling means; operative connections between said measuring means and said power operation controlling means comprising two levers relatively rotatable about a common fulcrum; means to maintain said two levers in alignment; means yieldingly to maintain said maintaining means in engagement with said two levers; and means to adjust the point of engagement of said maintaining means with said levers longitudinally of the latter.

9. Automatic controlling apparatus, more particularly for aircraft, comprising in combination, flight controlling means; measuring means to exert an automatic controlling action upon said flight controlling means; operative connections between said measuring means and said flight controlling action upon said controlling means comprising two levers rotatable about'a common fulcrum; means to maintain said two levers in alignment; means yieldingly to maintain said maintaining means in engagement with said two levers; means to adjust the point of engagement of said maintaining means with said levers longitudinally of the latter; and means to hold said maintaining means in adjusted position.

10. Automatic controlling apparatus, more particularly for aircraft comprising in combination, flight controlling means; measuring means to exert an automatic controlling action upon said flight controlling means; operative connections between said flight controlling means and said measuring means comprising two levers rotatable about a common fulcrum; means to maintain said j two levers in alignment; resilient means yieldingly to maintain said maintaining means in engagement with said two levers; and means permitting adjustment of said resilient means relatively to said maintaining means.

11. Automatic controlling apparatus, more particularly for aircraft, comprising in combination, flight controlling means; measuring means to exert an automatic controlling action upon said flight controlling means; operative connections between said measuring means and said flight controlling means comprising two levers rotatable about a common fulcrum; means to maintain said two levers in alignment; resilient means yieldingly to maintain said. maintaining means in engagement with said two levers; and means variably to adjust the tension of said resilient means.

12. Automatic controlling apparatus, more particularly for aircraft, comprising in combination, flight controlling means; measuring means to exert an automatic controlling action upon said flight controlling means; and means including a resilient connection and damping means in the operative connection between said measuring means and said flight controlling means.

WALDEMAR 

